High Fidelity Analysis of a Generic Supersonic Combustor with a Single Open Cavity

Reynolds-Averaged Navier-Stokes simulations using a k-ω model are employed to explore an analogous supersonic combustor configuration with a single cavity flame-holding. The flight conditions replicate those used on a typical hydrocarbon hypersonic air-breathing propulsion system at approximately Mach 6 and 26 km altitude. The combustor cross- section is rectangular in shape, and selected for studying a typical scramjet flow-path as in a direct connect facility. The hypersonic inlet is assumed to precondition the air past the isolator to enter the study configurations at Mach 2.2, with a corresponding Re ~8.8x10 6 m -1 . Three numerical calculations were performed, where the fuel was injected at an angle of 30 o

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